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GIII BL207 AIRFOIL (giiih-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GIII BL207 AIRFOIL (giiih-il)
Reynolds number: 100,000
Max Cl/Cd: 47.68 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-giiih-il-100000.txt
Download as CSV file: xf-giiih-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GIII BL207 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5849   0.09626   0.09152  -0.0159   1.0000   0.0803
  -8.500  -0.5972   0.09252   0.08775  -0.0214   1.0000   0.0807
  -8.250  -0.6078   0.08954   0.08458  -0.0251   1.0000   0.0811
  -8.000  -0.4817   0.07315   0.06874  -0.0214   1.0000   0.0994
  -7.750  -0.4888   0.06885   0.06447  -0.0232   1.0000   0.1020
  -7.500  -0.4997   0.06449   0.06009  -0.0252   1.0000   0.1051
  -7.250  -0.5236   0.06073   0.05605  -0.0289   1.0000   0.1085
  -7.000  -0.5107   0.05500   0.05050  -0.0273   1.0000   0.1119
  -6.750  -0.5052   0.05131   0.04678  -0.0267   1.0000   0.1182
  -6.500  -0.5493   0.05965   0.05456  -0.0254   1.0000   0.1183
  -6.250  -0.5418   0.05596   0.05074  -0.0254   1.0000   0.1268
  -6.000  -0.5334   0.05298   0.04755  -0.0249   1.0000   0.1391
  -5.750  -0.5236   0.05015   0.04460  -0.0238   1.0000   0.1529
  -5.500  -0.5130   0.04719   0.04162  -0.0223   1.0000   0.1685
  -5.250  -0.5052   0.04498   0.03934  -0.0204   1.0000   0.1954
  -5.000  -0.4820   0.02855   0.02364  -0.0158   1.0000   0.2137
  -4.750  -0.4790   0.02618   0.02126  -0.0130   1.0000   0.2405
  -4.250  -0.4169   0.02965   0.02134  -0.0129   1.0000   0.0797
  -4.000  -0.3970   0.02686   0.01830  -0.0114   1.0000   0.0765
  -3.750  -0.3761   0.02517   0.01622  -0.0098   1.0000   0.0786
  -3.500  -0.3539   0.02360   0.01428  -0.0083   1.0000   0.0799
  -3.250  -0.3306   0.02212   0.01249  -0.0071   1.0000   0.0809
  -3.000  -0.3064   0.02014   0.01051  -0.0064   1.0000   0.0851
  -2.750  -0.2839   0.01940   0.00961  -0.0054   1.0000   0.0946
  -2.500  -0.2605   0.01802   0.00839  -0.0047   1.0000   0.1030
  -2.250  -0.2381   0.01714   0.00760  -0.0039   1.0000   0.1182
  -2.000  -0.2158   0.01634   0.00686  -0.0031   1.0000   0.1351
  -1.750  -0.0354   0.01323   0.00643  -0.0238   1.0000   1.0000
  -1.500  -0.0424   0.01325   0.00638  -0.0188   1.0000   1.0000
  -1.250  -0.0534   0.01327   0.00636  -0.0133   1.0000   1.0000
  -1.000  -0.0620   0.01328   0.00631  -0.0082   1.0000   1.0000
  -0.750  -0.0635   0.01333   0.00626  -0.0042   1.0000   1.0000
  -0.500  -0.0562   0.01344   0.00625  -0.0017   1.0000   1.0000
  -0.250  -0.0429   0.01362   0.00631  -0.0002   1.0000   1.0000
   0.000  -0.0148   0.01390   0.00648  -0.0015   0.9968   1.0000
   0.250   0.0307   0.01426   0.00672  -0.0059   0.9884   1.0000
   0.500   0.0788   0.01461   0.00699  -0.0108   0.9792   1.0000
   0.750   0.1301   0.01492   0.00726  -0.0161   0.9697   1.0000
   1.000   0.1741   0.01515   0.00749  -0.0200   0.9585   1.0000
   1.250   0.2178   0.01537   0.00772  -0.0237   0.9479   1.0000
   1.500   0.2675   0.01553   0.00794  -0.0284   0.9388   1.0000
   1.750   0.3171   0.01561   0.00812  -0.0329   0.9286   1.0000
   2.000   0.3596   0.01567   0.00828  -0.0359   0.9164   1.0000
   2.250   0.4005   0.01569   0.00841  -0.0383   0.9038   1.0000
   2.500   0.4384   0.01567   0.00855  -0.0399   0.8904   1.0000
   2.750   0.4727   0.01562   0.00863  -0.0406   0.8759   1.0000
   3.000   0.5037   0.01553   0.00867  -0.0404   0.8601   1.0000
   3.250   0.5337   0.01524   0.00853  -0.0392   0.8420   1.0000
   3.500   0.5550   0.01474   0.00810  -0.0357   0.8128   1.0000
   3.750   0.5735   0.01429   0.00770  -0.0317   0.7787   1.0000
   4.000   0.5938   0.01395   0.00740  -0.0285   0.7456   1.0000
   4.250   0.6132   0.01368   0.00716  -0.0254   0.7038   1.0000
   4.500   0.6324   0.01352   0.00701  -0.0224   0.6478   1.0000
   4.750   0.6494   0.01362   0.00688  -0.0190   0.5516   1.0000
   5.000   0.6532   0.01535   0.00712  -0.0141   0.2933   1.0000
   5.250   0.6595   0.01808   0.00855  -0.0110   0.1376   1.0000
   5.500   0.6763   0.01963   0.00988  -0.0091   0.1089   1.0000
   5.750   0.6959   0.02119   0.01133  -0.0076   0.0946   1.0000
   6.000   0.7177   0.02273   0.01287  -0.0065   0.0827   1.0000
   6.250   0.7424   0.02503   0.01501  -0.0058   0.0761   1.0000
   6.500   0.7681   0.02676   0.01705  -0.0049   0.0714   1.0000
   6.750   0.7916   0.02880   0.01909  -0.0043   0.0649   1.0000
   7.000   0.8152   0.03198   0.02259  -0.0034   0.0630   1.0000
   7.250   0.8365   0.03485   0.02594  -0.0020   0.0625   1.0000
   7.500   0.8550   0.03789   0.02955  -0.0003   0.0618   1.0000
   7.750   0.8699   0.04090   0.03313   0.0015   0.0600   1.0000
   8.000   0.8826   0.04503   0.03771   0.0032   0.0611   1.0000
   8.250   0.8981   0.05072   0.04352   0.0039   0.0641   1.0000
   9.500   0.6364   0.08884   0.08427  -0.0043   0.1787   1.0000
   9.750   0.6402   0.09296   0.08840  -0.0039   0.1736   1.0000
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